Short takeoff jump mode for aircraft landing gear struts

B - Operations – Transporting – 64 – C

Patent

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244/54, 244/79

B64C 25/26 (2006.01)

Patent

CA 1271734

ABSTRACT OF THE DISCLOSURE A telescoping landing gear shock strut set which can provide both the main landing gear and auxiliary landing gear function, and which is affixed to and extendible from an aircraft, is restrained in an unenergized, compressed condition. A high pressure gas charge is then provided between the extendible element of the strut and the element affixed to the aircraft. Early in the takeoff run, the charge gas in the forward strut is released so as to pump the nose and rotate the aircraft to a high angle of attack appropriate for takeoff. Subsequent to this rotation, but before the conventional takeoff speed is reached, the charge gas in the main strut is released to impart a vertical velocity to the entire aircraft, thus jumping it into the air. Both the forward strut and main struts incorporate a hydraulic flow bypass function, so that the landing shock absorption function does not comprise the aforesaid energy release. The struts also incorporate valves to discharge enough residual gas immediately at the end of the jump stroke so that the landing energy absorption mode is not compromised. Following the main gear jump, the continuining horizontal acceleration provided by the propulsion engines, and continuously weakening vertical acceleration comprising gravity diminished by the wing aerodynamic lift, which is increasing with speed, results in an initially upward aircraft trajectory which does not return to earth. A takeoff run with the aforesaid jump action is considerably shorter than the takeoff run without the jump function. Although the jump takeoff speed is less than the conventional takeoff speed, and there would be a lift shortage in a straight flight path, the centrifugal acceleration produced by the bending downward of trajectory, which is initially inclined upward, compensates for this temporary lift shortage.

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